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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 500,000
Max Cl/Cd: 133.91 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377-il-500000.txt
Download as CSV file: xf-e377-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1385   0.09412   0.09173  -0.0317   0.8418   0.0088
  -7.250  -0.1342   0.09296   0.09037  -0.0315   0.7965   0.0089
  -7.000  -0.1238   0.09131   0.08860  -0.0333   0.7722   0.0089
  -6.750  -0.1115   0.08922   0.08641  -0.0352   0.7526   0.0089
  -6.500  -0.0773   0.07195   0.06909  -0.0295   0.6944   0.0091
  -6.250  -0.0673   0.06811   0.06522  -0.0300   0.6848   0.0092
  -6.000  -0.0715   0.08030   0.07729  -0.0400   0.7095   0.0091
  -5.750  -0.0584   0.07724   0.07418  -0.0410   0.6980   0.0093
  -5.500  -0.0425   0.07471   0.07160  -0.0428   0.6861   0.0095
  -5.250  -0.0246   0.07227   0.06911  -0.0452   0.6762   0.0097
  -5.000  -0.0052   0.06982   0.06660  -0.0478   0.6675   0.0099
  -4.750   0.0160   0.06733   0.06408  -0.0508   0.6583   0.0103
  -4.500   0.0386   0.06480   0.06148  -0.0539   0.6510   0.0106
  -4.250   0.0629   0.06222   0.05885  -0.0573   0.6429   0.0112
  -4.000   0.0895   0.05962   0.05620  -0.0610   0.6362   0.0119
  -3.750   0.1280   0.05745   0.05395  -0.0673   0.6284   0.0128
  -3.500   0.1650   0.05504   0.05145  -0.0732   0.6218   0.0130
  -3.250   0.1985   0.05136   0.04771  -0.0783   0.6156   0.0132
  -3.000   0.2139   0.04836   0.04466  -0.0784   0.6099   0.0140
  -2.750   0.2431   0.04619   0.04246  -0.0814   0.6034   0.0152
  -2.500   0.2768   0.04384   0.04000  -0.0853   0.5975   0.0161
  -2.250   0.3133   0.04148   0.03757  -0.0896   0.5919   0.0175
  -2.000   0.3637   0.03983   0.03578  -0.0960   0.5861   0.0189
  -1.750   0.4027   0.03767   0.03348  -0.1000   0.5810   0.0190
  -1.500   0.4312   0.03387   0.02966  -0.1028   0.5756   0.0202
  -1.250   0.4614   0.03224   0.02794  -0.1047   0.5704   0.0219
  -1.000   0.5037   0.03093   0.02648  -0.1083   0.5656   0.0267
  -0.750   0.5448   0.02959   0.02502  -0.1114   0.5602   0.0273
  -0.500   0.5821   0.02624   0.02151  -0.1149   0.5556   0.0283
  -0.250   0.6093   0.02487   0.02009  -0.1157   0.5508   0.0296
   0.000   0.6407   0.02361   0.01876  -0.1170   0.5458   0.0317
   1.000   0.7937   0.01332   0.00725  -0.1243   0.5286   0.0276
   1.250   0.8248   0.01133   0.00466  -0.1248   0.5246   0.0266
   1.500   0.8533   0.01062   0.00375  -0.1247   0.5199   0.0270
   1.750   0.8812   0.01008   0.00308  -0.1244   0.5152   0.0302
   2.000   0.9084   0.01002   0.00295  -0.1241   0.5110   0.0373
   2.250   0.9359   0.01006   0.00302  -0.1239   0.5064   0.0622
   2.500   0.9631   0.01009   0.00307  -0.1236   0.5015   0.0720
   2.750   0.9900   0.01016   0.00308  -0.1234   0.4972   0.0799
   3.000   1.0171   0.01027   0.00321  -0.1231   0.4926   0.0889
   3.250   1.0442   0.01020   0.00317  -0.1229   0.4877   0.0956
   3.500   1.0710   0.01027   0.00319  -0.1226   0.4832   0.1035
   3.750   1.0980   0.01027   0.00325  -0.1224   0.4781   0.1156
   4.000   1.1249   0.01029   0.00333  -0.1221   0.4725   0.1297
   4.250   1.1515   0.01039   0.00343  -0.1218   0.4672   0.1459
   4.500   1.1784   0.01040   0.00353  -0.1216   0.4611   0.1619
   4.750   1.2050   0.01049   0.00363  -0.1213   0.4554   0.1793
   5.000   1.2316   0.01056   0.00378  -0.1211   0.4495   0.2006
   5.250   1.2582   0.01062   0.00394  -0.1209   0.4432   0.2265
   5.500   1.2846   0.01072   0.00411  -0.1206   0.4372   0.2608
   5.750   1.3110   0.01075   0.00428  -0.1204   0.4301   0.3201
   6.000   1.3397   0.01013   0.00444  -0.1208   0.4230   1.0000
   6.250   1.3659   0.01026   0.00462  -0.1205   0.4152   1.0000
   6.500   1.3919   0.01043   0.00480  -0.1202   0.4073   1.0000
   6.750   1.4176   0.01062   0.00498  -0.1198   0.3982   1.0000
   7.000   1.4435   0.01078   0.00519  -0.1195   0.3887   1.0000
   7.250   1.4690   0.01098   0.00542  -0.1192   0.3783   1.0000
   7.500   1.4943   0.01122   0.00570  -0.1188   0.3669   1.0000
   7.750   1.5190   0.01150   0.00596  -0.1184   0.3461   1.0000
   8.000   1.5423   0.01197   0.00632  -0.1179   0.3156   1.0000
   8.250   1.5644   0.01263   0.00682  -0.1173   0.2776   1.0000
   8.500   1.5833   0.01376   0.00763  -0.1165   0.2231   1.0000
   8.750   1.6001   0.01514   0.00866  -0.1155   0.1689   1.0000
   9.000   1.6171   0.01639   0.00969  -0.1145   0.1280   1.0000
   9.250   1.6323   0.01778   0.01082  -0.1132   0.0887   1.0000
   9.500   1.6457   0.01928   0.01207  -0.1118   0.0543   1.0000
   9.750   1.6512   0.02147   0.01393  -0.1095   0.0154   1.0000
  10.000   1.6610   0.02302   0.01547  -0.1074   0.0075   1.0000
  10.250   1.6736   0.02412   0.01671  -0.1056   0.0066   1.0000
  10.500   1.6833   0.02534   0.01806  -0.1035   0.0062   1.0000
  10.750   1.6866   0.02664   0.01951  -0.1005   0.0059   1.0000
  11.000   1.6863   0.02823   0.02124  -0.0977   0.0057   1.0000
  11.250   1.6841   0.03029   0.02342  -0.0954   0.0055   1.0000
  11.500   1.6808   0.03280   0.02606  -0.0938   0.0052   1.0000
  11.750   1.6760   0.03580   0.02921  -0.0927   0.0050   1.0000
  12.000   1.6654   0.03974   0.03332  -0.0920   0.0047   1.0000
  12.250   1.6570   0.04367   0.03740  -0.0916   0.0046   1.0000
  12.500   1.6486   0.04773   0.04161  -0.0915   0.0045   1.0000
  12.750   1.6435   0.05148   0.04549  -0.0914   0.0045   1.0000
  13.000   1.6368   0.05550   0.04964  -0.0915   0.0045   1.0000
  13.250   1.6303   0.05960   0.05386  -0.0917   0.0044   1.0000
  13.500   1.6230   0.06384   0.05824  -0.0920   0.0044   1.0000
  13.750   1.6157   0.06820   0.06273  -0.0924   0.0044   1.0000
  14.000   1.6094   0.07256   0.06721  -0.0929   0.0043   1.0000
  14.250   1.6037   0.07698   0.07177  -0.0936   0.0043   1.0000
  14.500   1.5973   0.08160   0.07652  -0.0943   0.0042   1.0000
  14.750   1.5916   0.08623   0.08128  -0.0951   0.0042   1.0000
  15.000   1.5861   0.09092   0.08613  -0.0961   0.0041   1.0000
  15.250   1.5806   0.09568   0.09104  -0.0971   0.0040   1.0000
  15.500   1.5750   0.10056   0.09606  -0.0983   0.0040   1.0000
  15.750   1.5691   0.10560   0.10125  -0.0996   0.0039   1.0000
  16.000   1.5629   0.11081   0.10661  -0.1011   0.0039   1.0000
  16.250   1.5561   0.11622   0.11218  -0.1028   0.0039   1.0000
  16.500   1.5489   0.12185   0.11799  -0.1049   0.0039   1.0000
  16.750   1.5410   0.12776   0.12407  -0.1072   0.0039   1.0000
  17.000   1.5321   0.13402   0.13051  -0.1100   0.0039   1.0000
  17.250   1.5224   0.14065   0.13731  -0.1132   0.0039   1.0000
  17.500   1.5125   0.14754   0.14438  -0.1168   0.0040   1.0000
  17.750   1.5027   0.15457   0.15157  -0.1207   0.0040   1.0000
  18.000   1.4913   0.16228   0.15946  -0.1254   0.0040   1.0000
  18.250   1.4811   0.16984   0.16718  -0.1301   0.0041   1.0000
  18.500   1.4706   0.17779   0.17528  -0.1352   0.0042   1.0000
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